Fuel tank for aeroplanes and the like



April 28, 1925.

M. GARAGNANI FUEL TANK FOR AEROPIJANES AND THE LIKE Filed Marbh 14, 1924 2 Sheets-Sheet 1 J/arz'a fiarajnalzi Quito: new 5 April 28, 1925.

M. GARAGNANI FUEL TANK FOR AEROPLANES ANDJFHE LIKE Filed Maz ch 14. 1924 2 Sheets-Sheet 2 Patented Apr. 28, 1925.

1 UNITED STATES PATENT. OFFICE.

M ARIO GARAGNANI, 0F PARIS FRANCE, ASSIGNOR O F ONE HALF 1'0 HENRY A. DE

MAILLY, OF NEW YORK, N. Y.

TANK FOR AEROPLANES AND THE LIKE.

Application filed March 14, 1924. Serial No. 699,339.

To all whom it may concern:

Be it known that MARIO GARAGNANI, a citizen of the Republic of Costa Rica, residing at Paris, France, has invented certain new and useful Improvements in Fuel ,Tanks for Aeroplanes and the like, of which the following is a specification.

This invention relates to new and useful improvements in fuel tanks, particularly applicable to military aeroplanes and the like, and the primary object of the invention is to provide certain new and useful improvements in my French Patent No. 557,644., issued to me May 8, 1923 One of the principal objects resides in the construction of a tank, particularly adapted to contain gasoline which will prevent the leakage of the fuel therefrom upon being pierced or struck by shell, shrapnel or other projectile.

A still further object of this invention resides in constructing the tank in such a manner that when pierced or struck by a .projectile the opening formed therein will be quickly-andreadily closed to prevent the escape or leakageof the fuel therefrom.

A further object resides in constructing a tank of two walls, having relative movement with respect-to one another, which movement isaut-omatic upon the piercing or strikingof the walls by a projectile.

Still} another object of the invention resides in providing a means for raising and lowering the tank with respect to its support and the provision of a further means forautomatically disconnecting the tank upon itsbeing lowered, so that said tank may be dropped from the aeroplane or airship to prevent the latter from being enveloped in flames should an explosion take lace.

p A still further object resides in providing a device of this character which is simple and durable in construction, comparatively inexpensive to manufacture, and one which will be very efficient and useful in operation.

With these and other objects in view my invention. consists in the novel features of construction, the combination and arrangement of parts as will be hereinafter referred to and more particularly pointed out in the specification and claims.

In the accompanying drawings, forming a means whereby the two tank sections may be moved with relation to one another.

Figure 4 is a transverse section as seen on the line H of Fig. 3.

Figure 5 is an enlarged detail section showing the latch members retaining the tank in position between the guides or supports and also illustrating the latch member retaining the suspension cables in connection with the tank.

Figure 6 is an enlarged detail side elevation, partly in section, showing the connectlon between the conduit releasing means and the operating mechanism'therefor, and

Figure 7 is a fragmentary detail plan View of the top of the inner section of the tank showing the annular opening therein and the webs.

It has been my experience in the art of aviation for military purposes to note that a great many lives and planes have been lost as the result of fires-caused by explosions in the fuel tanks, directly resulting from being struck by projectiles. WVhere explosions have not taken place, accidents have occurred by reason of leakage of gasoline from the tanks after having been pierced r by a projectile.

With this in mind, I have invented the present device which will overcome the difii culties heretofore experienced in military aviation and will lessen the danger of loss of lives and planes as the result of tanks being struck by projectiles.

To this end I provide a tank or reservoir 1 which is provided with inner and outer sections 2 and 3, respectively. Each section in itself constitutes a complete enclosure and said sections fit snugly, one within the other, as clearly illustrated in Fig. 1 of the drawings. The outer section 3 is secured at its to the inner section 2 of the tank or reservoir. This sleeve is internally threaded and has introduced therein a plug or the like 7. The fuel may be introduced to the tank through the bore of the sleeve 6 and said tank is, of course, closed by this plug 7 The section 2 is adapted for relative movement with respect to the section 3, the sleeve 6 moving with said inner section 2, as appears obvious. ment and its purposes will be hereinafter more particularly described.

I desire ,at this time to specifically describe the construction of the walls forming the sections 2 and 3 of this reservoir. The outer wall or section 3 is composed of an outer layer of papier mach or other paper pulp material 8, which has considerable elasticity and stiffness. Applied to the inner face of this outer coating or layer is a layer of agglomerated cork mixed with rubber and possibly solidified or stiffened by other materials, the latter layer being designated by the numeral 9. Superimposed on the inner face of this cork layer is a layer of rubber designated by the numeral 10, which rubber layer is intended to serve in closing holes or openings caused by the passage of a projectile through the reservoir.

The inner wall or section 2, comprises an' inner very thin lining of copper designated as 11,,the copper serving to prevent the liquid from entering the other layers hereinafter describedr On the outer face of this inner layer of copper is applied a layer of agglomerated cork mixed with rubber and stiffened by other materials, the latter layer being designated by the numeral 12, and superimposed on the latter layer is a rubber layer 13, similar to the layer 10 of the outer section 3. These two rubber layers 10 and 13 cooperate with one another to form a seal or the like for openings or holes caused by the passage of projectiles through the reservoir or tank. These two layers 10 and 13are adapted to contact lightly with one another and in order to prevent friction in the movement of the two sections 2 and 3 with respect to one another, I desire to introduce between said layers 10 and 13 a thin film of glycerinc or other lubricating oil. the purpose of which appears obvious. While I have particularly descr bed the elements The manner of such moveconstituting the material of which the sections of the tank are composed, I may state generally that these sections of said tank are formed of fibrous material. 4

As previously stated, this invention is contemplated for use in connection with aeroplanes or airships but may be used in connection with motor vehicles, if desired. For purposes of illustration I shall refer to its use as applied to aeroplanes or ail-ships.

The tank or reservoir proper is adapted to be movably supported between a pair of vertical guide rails or the like 14 and 15, which are carried on the frame or fuselage of the machine. Extending laterally from the tank or reservoir 1 at diametrically opposite points thereon are the guide blocks 16. These blocks are preferably arranged in pairs and are provided withrecesses or notches 17 which are adapted to receive therein spring-forced latch members or pins 18, the latter operating laterally through the vertical guide rails 14 and 15. These latch I pins are connected with flexible connections or cables 19 which lead to any distant point orto a point adjacent the pilots seat to be readily actuated by the pilot when it is desired to release the tank from its support.

Under normal conditions the tank is supported in place as show-n in Fig. 1, and when said tank is struck by a projectile causing explosion, the pilot may release the tank to prevent the plane from being enveloped in flames. The pilot then draws upon the cables 19, which are preferably connected together in any preferred manner (not shown), and the pins or latch members 18 are released from engagement with the blocks 16 so that the tank may be lowered in its guideways by gravity. Connected with one or more of the blocks 16 is a cable 20 which extends over a pulley 21 supported on one of the guide rails and extends to a drum or pulley 22 at the lower end of the last mentioned guide rail, as clearly shown in Fig. 1 of the drawings. Carried on the shaft 23 supporting the drum 22 is a worm 24 which meshes with a rack 25 formed peripherally on a sleeve or the like 26. This sleeve 26 is internally threaded from opposite ends in opposite directions, similar to a turn buckle construction, and the one. end thereof is engaged with the threaded end 27 of the feed pipe 5. Thus it will be seen, that as the tank or reservoir is being lowered the end of the feed pipe 5 is being disconnected automatically so that when the tank is ready to be dropped from its support this pipe will not interfere there with. The opposite end of the sleeve 26 connects with a pipe 28 which leads to the carburetor of the engine (not shown). This construction is shown in Fig. 1 of the drawings and in detail in Fig. 6.

It is, of course, also necessary in releas:

gagement with the latch 29. It is obvious from'this construction that as the tank is lowered the latch member 29 will have its beveled end 31 contact with the cam 32 and forcing the same inwardly against the tension of the actuated spring will obviously release the cable 20 from the hook member 30. The device is so constructed that the end 27 of the feed pipe 5 will be disconnected from the member 26 prior to the time the latch 30 contacts with the cam 32, so

that when the cable 20'is disconnected, there will be'no further interference with the releasing of the tank entirely from its support on the machine. It will thus be seen that quick and ready release of the tank may be obtained in the event of necessity which will prevent the loss of the plane and the loss of the lives of the pilot and observer, should an explosion occur when said tank is struck by a projectile. After the tank has been re leased the pilot, if competent, may vol-plane 'or otherwise bring the ship safely to the ground.

I have described hereabove the means for releasing the tank in the event of fire occurring upon the striking of the tank by a projectile, but it frequently occurs that a fire or explosion will not take place when the tank is pierced or struck by a projectile. I have provided a means for use under such conditions which will permit of the pilot continuing in his course Without danger of the escape or leakage of gasoline.

In carrying out this idea I have provided the tank, as previously described, with an inner 'and outer section, the inner section being movable rotatably with respect to the outer section.

Thus whenthe Walls of the sections are pierced the inner section may be moved to prevent the openings in the two sections from registering and the projectile holes or openings will thus be closed. In

view of the particularcharacter of wall construction with the inner opposed rubber layers, the holes formed in the two sections will be substantially sealed and, obviously, there will be no leakage of gasoline.

I provide an automatic means for causing the rotation of the inner section with respect to the outer section of the tank. The outer periphery of the sleeve 6 at its upper edge is formed with a rack 33, the teeth of which engage the teeth on a pinion or annulus 34. Connected with this pinion 34 is a coiled spring 35, tightly Wound and having a tendency to rotate said pinion or annulus 34. The spring 35 and the pinion 34 connect with a shaft 36, supported on a beam or the like 37 of the frame or fuselage of the machine. Also supported on this beam 37 are the shafts 38 and 39 which respectively support the pinions 40 and 41, the latter meshing with one another and also meshing in turn with the pinion 34, as clearly shown in Figs. 1 and 2 of the drawings.

In alignment with the train of gears and projecting from the guide rail 14 is an arm 42, from which projects an upstanding lug 43, and pivotally supported on'said lug is a detent 44 which is adapted to rest at its outer end upon the upper face of the gear-.

or. pinion 40, as clearly shown in Fig. 3. A stop pin 45 is provided on the upper face of the gear 40-to contact with the detent 44. With the tendency of the gears to rotate under the action of the spring 35, it is obvious that the detent 44 positioned as shown in Fig. 1 and in full lines in Fig. 3 will pregaged atits ends respectively with the arm vent such rotation. A coiled spring 46 en- 42 and the detent 44 normally retains said A cylindrical casing 50 is secured to the outer face of the top o-fthe' outer section 3 of the tank to coverthe opening 49 and a check valve 51 within said casing and actuated by means of a coiled spring 52 is adapt! ed to normally close the opening 49. This check valve is provided with a stem 53 extending beyond the casing 50, and in vertical alignment with the detent 44.

Upon being struck by a projectile a certain obvious pressure takes place within the tank or reservoir'and this pressure is sufficient to unseat the valve 51, forcing the same upward against the tension of the spring 52.

Upon upward movement 'of the valve the stem will contact'with the detent 44 and raise the latter as shown in dotted lines in Fig. 3 of the drawings. This action will permit of the train of gears to be rotated under the action ofthe spring. 35 but only a single rotation of the gear 40 may occur, as the valve 51 will return to its initial position quickly after the impact has occurred. A single rotation of the gear 40, however, will obviously cause the inner section 2 of the tank to be rotated sufficiently to take the openings formed by the projectile out of registration. This will prevent leakage of the fuel from the tank and permit of the pilot continuing on his course igvithout the necessity of landing. This phase of the operation of the device is automatic, as appears obvious.

It will be seen from the foregoing detailed description of the construction and operation of my invention that I have provided a simple, inexpensive, and efiicient means for carrying out the objects of the invention, and while I have described the elements best adapted to perform the functions set forth, it is obvious that various changes in form, proportion and the minor details of construction may be made without departing from the spirit of the invention or sacrificinglany oft-he principles of'the. invention.

aving thus described my invention, what I claim is 1. A fuel tank comprising inner and outer contacting sections having relative "movement.

I 2. A fuel tank comprising inner and outer contacting sections, the inner section being capable of rotary movement with respect to the outer section.

,3. In combination with a support; of a tank comprising inner and outer sections, the inner section being rotatably movable with respect to the outer section, and means for automatically giving rotary movement to the inner section upon impact of a projectile against the tank.

.4. A tank comprising inner and outer sections, the inner section movable rotatably with respect to the outer section, the walls of said sections being formed of superimposed layers. and a lubricant interposed between the walls of the two sections.

i 5. A tank comprising inner and outer sections, the inner section being rotatable with respect to the outer section, the walls of each of said-sections being formed of superimposed layers and the inner opposed layers of said sections being formed of rubber, and a lubricant interposed between the rubber layers of said sections.

6. A tank comprising inner and outer sections, the inner section being movable with respect to the outer section, the wall of said inner section being composed of an inner lining of copper, an intermediate layer of cork, and an outer layer of rubber, and the wall of the outer section being formed of an inner layer of rubber, an intermediate layer of cork and an outer layer of paper pulp.

7. A tank comprising inner and outer sections, the inner section being rotatable with respect to the outer section, a train of gears having connection with said inner section. means for locking the movement of said gears, and additional means for automatir cally releasing the last mentioned locking means upon the impact of a projectile against the tank.

8. A tank comprising inner and outer sections, the inner section being rotatable with respect to the outer section, a train of gears in connection with said inner section, means for locking said gears against rotation, and a check valve carried on the outer section and adapted for cooperation with the last mentioned locking nieans. and the interior of the inner section to automatically release the locking means and permit rotation of the inner section upon impact of a projectile against the tank.

9. The combination with a support; of a tank movable vertically thereon, said tank comprising inner and outer contacting sections, the inner section being capable of rotary movement with respect to the outer section, means for locking the outer section of the tank. in rigid position on the support, and means for releasing the last mentioned locking means.

10. The combination with a support; of a tank movably mounted thereon, said tank comprising inner and outer sections. the inner section being capable of rotary movement with respect to the outer section, means for automatically causing rotation of said inner section upon impact of a projectile against the tank, means for locking the outer section rigidly on the support, and means for releasing the last mentioned locking means.

11. A fuel tank comprising inner and outer sections contacting throughout their surfaces and having relative movement.

In .testimony whereof I atfix my signature.

MARIO GARAGNANI. 

